ED Decision 2003/18/RM
The wing and wing bracing must be designed for the following loading conditions:
(a) Unsymmetrical wing loads. Unless the following values result in unrealistic loads, the rolling accelerations may be obtained by modifying the symmetrical flight conditions in CS-VLA 333(d) as follows:
In condition A, assume that 100% of the semispan wing airload acts on one side of the aeroplane and 70% of this load acts on the other side.
(b) The loads resulting from the aileron deflections and speeds specified in CS-VLA 455, in combination with an aeroplane load factor of at least two thirds of the positive manoeuvring load factor used for design. Unless the following values result in unrealistic loads, the effect of aileron displacement on wing torsion may be accounted for by adding the following increment to the basic aerofoil moment coefficient over the aileron portion of the span in the critical condition determined in CS-VLA 333(d);
where -
∆Cm is the moment coefficient increment; and
δ is the down aileron deflection in degrees in the critical condition.